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研究了飞船推进系统推力室工作过程。用一甲基肼作燃料 ,四氧化二氮为氧化剂。数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等。利用压力隐式算子分裂 ( PISO)计算方法 ,在任意曲线坐标下采用非交错网格技术 ,成功地获得了 3种推力室工作过程的流场参数 ,为飞船推进系统工作过程稳定性分析提供了理论依据。
Studied the spacecraft propulsion system thrust chamber work process. With methylhydrazine as a fuel, nitrous oxide as an oxidant. The numerical simulation model considers the atomization mechanism of spontaneous combustion propellant, high-pressure decomposition combustion and pre-mixed flow turbulent combustion. Using pressure implicit operator splitting (PISO) method and non-staggered grid technique under arbitrary curvilinear coordinates, the flow field parameters of three kinds of thrust chamber work were successfully obtained, providing the stability analysis of the working process of spacecraft propulsion system The theoretical basis.